CA2649070A1 - Apparatus and method for producing a large-area fibre-composite structural component - Google Patents

Apparatus and method for producing a large-area fibre-composite structural component Download PDF

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Publication number
CA2649070A1
CA2649070A1 CA002649070A CA2649070A CA2649070A1 CA 2649070 A1 CA2649070 A1 CA 2649070A1 CA 002649070 A CA002649070 A CA 002649070A CA 2649070 A CA2649070 A CA 2649070A CA 2649070 A1 CA2649070 A1 CA 2649070A1
Authority
CA
Canada
Prior art keywords
laying
shaping element
predetermined
fibrous sheet
turning
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CA002649070A
Other languages
French (fr)
Other versions
CA2649070C (en
Inventor
Jorg Schendel
Bernd Ostermeier
Thomas Konsolke
Ralf-Peter Dittmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
Original Assignee
Airbus Deutschland Gmbh
Jorg Schendel
Bernd Ostermeier
Thomas Konsolke
Ralf-Peter Dittmann
Airbus Operations Gmbh
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Deutschland Gmbh, Jorg Schendel, Bernd Ostermeier, Thomas Konsolke, Ralf-Peter Dittmann, Airbus Operations Gmbh filed Critical Airbus Deutschland Gmbh
Publication of CA2649070A1 publication Critical patent/CA2649070A1/en
Application granted granted Critical
Publication of CA2649070C publication Critical patent/CA2649070C/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B29C70/386—Automated tape laying [ATL]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
    • B29K2995/0037—Other properties
    • B29K2995/0094—Geometrical properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B29L2031/3082—Fuselages
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/17—Surface bonding means and/or assemblymeans with work feeding or handling means
    • Y10T156/1788—Work traversing type and/or means applying work to wall or static structure
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/17—Surface bonding means and/or assemblymeans with work feeding or handling means
    • Y10T156/1788—Work traversing type and/or means applying work to wall or static structure
    • Y10T156/1795—Implement carried web supply

Abstract

The present invention provides an apparatus and a method for producing a large-area fibre-composite structural component, in particular for the aircraft sector, comprising a predetermined shaping element (1) , a controllable laying device (4, 5, 6) for the defined laying of at least one fibrous sheet (15) over or into the predetermined shaping element (1) , a controllable turning device (10) for a defined turning of the predetermined shaping element (1) and of the laying device (4, 5, 6} in relation to each other by a predetermined turning angle, and a central control device, which is connected to the laying device (4, 5, 6) and the turning device (10) for controlling of the same.

Claims (19)

1. Apparatus for producing a large-area fibre-composite structural component, in particular for the aircraft sector, comprising:
a predetermined shaping element (1);
a controllable laying device (4, 5, 6) for the defined laying of at least one fibrous sheet (15) over or into the predetermined shaping element (1), the laying device (4, 5, 6) having four synchronously controllable lifting columns (4), which are arranged in pairs around the shaping element (1), each pair of lifting columns (4) being respectively assigned a vertically adjustable cross member (5), wherein in each cross member (5) there are respectively integrated two receiving carriages (6) for receiving predetermined fibrous sheet rolls (2, 3) that can be displaced synchronously along the respective cross member (5);
a controllable turning device (10) for a defined turning of the predetermined shaping element (1) and of the laying device (4, 5, 6) in relation to each other by a predetermined turning angle; and a central control device, which is connected to the laying device (4, 5, 6) and the turning device (10) for controlling of the same.
2. Apparatus according to Claim 1, characterized in that the predetermined shaping element (1) has approximately the form of a turned-out, shallow dish.
3. Apparatus according to Claim 1 or 2, characterized in that the predetermined shaping element (1) has an oval or circular cross section.
4. Apparatus according to at least one of the preceding claims, characterized in that the predetermined shaping element (1) is formed suitably for the forming of a pressure dome of an aircraft.
5. Apparatus according to at least one of the preceding claims, characterized in that the receiving carriages (6) have an electronic drive device each that can be controlled by the central control device synchronously with the other receiving carriages (6).
6. Apparatus according to at least one of the preceding claims, characterized in that the central control device is connected to the lifting columns (4) for a synchronous vertical adjustment of the assigned cross members (5) along the longitudinal direction of the lifting columns (4) and to the receiving carriages (6) for a synchronous transverse adjustment of the receiving carriages (6) along the cross members (5).
7. Apparatus according to at least one of the preceding claims, characterized in that the laying device (4, 5, 6) has a transfer device for receiving the fibrous sheet (15), rolled up on two fibrous sheet rolls (2, 3), from a transporting car (8) in a defined transfer position.
8. Apparatus according to at least one of the preceding claims, characterized in that the turning device has a controllable turntable (10) for receiving and positioning the predetermined shaping element (1) in relation to the laying device (4, 5, 6).
9. Apparatus according to Claim 8, characterized in that the turntable (10) has an electronic drive device (11) that can be controlled by the central control device.
10. Apparatus according to at least one of the preceding claims, characterized in that the apparatus has an adjustable podium (13) for access to any region of the shaping element (1) by a member of the operating personnel.
11. Apparatus according to Claim 10, characterized in that the podium (13) is adjustable along a rail system and has at least one pivotable platform (14).
12. Apparatus according to at least one of the preceding claims, characterized in that the apparatus has a positioning device, for example a marking device, a linear laser projector system or the like, for positioning the fibrous sheet (15) to be laid and/or any additional reinforcing means in conjunction with the defined position of the turning device (10).
13. Apparatus according to at least one of the preceding claims, characterized in that the apparatus has in the event of failure of the automatic control by means of the central control device an emergency operating device for a manual emergency mode to perform the defined laying of the fibrous sheet (15).
14. Method for producing a large-area fibre-composite structural component, in particular for the aircraft sector, comprising the following method steps:
- provision of a predetermined shaping element (1);
- advance rolling up of a fibrous sheet (15) to be laid on two fibrous sheet rolls (2, 3), which are received by means of a controllable laying device (4, 5, 6) ;
- defined laying of the fibrous sheet (15) over or into the predetermined shaping element (1) by adjusting the two fibrous sheet rolls (2, 3) both in the vertical direction and in the transverse direction and guiding the two fibrous sheet rolls (2, 3) uniformly and synchronously from the centre of the predetermined shaping element (1) to the edge of the same by means of the controllable laying device (4, 5, 6);
- turning of the predetermined shaping element (1) and the controllable laying device (4, 5, 6) in relation to each other by a predetermined turning angle by means of a controllable turning device (10); and - defined laying of a further fibrous sheet on top of the already laid fibrous sheet (15) by means of the controllable laying device (4, 5, 6).
15. Method according to Claim 14, characterized in that the laying device (4, 5, 6) and the turning device (10) are controlled by a central control device.
16. Method according to Claim 14 or 15, characterized in that a number of fibrous sheets (15), for example six, are laid one on top of the other over or into the predetermined shaping element (1), after each laying of a fibrous sheet (15) the predetermined shaping element (1) being turned by means of the turning device (10) by a predetermined turning angle, by for example 30°, in relation to the laying device (4, 5, 6) and arrested.
17. Method according to at least one of Claims 14 to 16, characterized in that the two fibrous sheet rolls (2, 3) are guided in a self-supporting manner approximately 50 mm above the predetermined shaping element (1).
18. Method according to at least one of Claims 14 to 17, characterized in that a predetermined unrolling rate, a predetermined advancing rate and/or a predetermined advancing amount of the fibrous sheet (15) to be laid are controlled by the central control device during the laying of the same over or into the shaping element (1).
19. Method according to at least one of Claims 14 to 18, characterized in that, in the event of failure of the automatic control by means of the central control device, the laying device (4, 5, 6) is operated in an emergency mode for manual laying of the fibrous sheet (15).
CA2649070A 2006-05-05 2007-05-04 Apparatus and method for producing a large-area fibre-composite structural component Expired - Fee Related CA2649070C (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US79807106P 2006-05-05 2006-05-05
DE102006021110.3 2006-05-05
US60/798,071 2006-05-05
DE102006021110A DE102006021110B4 (en) 2006-05-05 2006-05-05 Apparatus and method for producing a large-scale fiber composite structural component
PCT/EP2007/054337 WO2007128788A1 (en) 2006-05-05 2007-05-04 Apparatus and method for producing a large-area fibre-composite structural component

Publications (2)

Publication Number Publication Date
CA2649070A1 true CA2649070A1 (en) 2007-11-15
CA2649070C CA2649070C (en) 2012-11-20

Family

ID=38564911

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2649070A Expired - Fee Related CA2649070C (en) 2006-05-05 2007-05-04 Apparatus and method for producing a large-area fibre-composite structural component

Country Status (11)

Country Link
US (1) US8088236B2 (en)
EP (1) EP2015922B1 (en)
JP (1) JP5027215B2 (en)
CN (1) CN101426636B (en)
AT (1) ATE489221T1 (en)
BR (1) BRPI0712293A2 (en)
CA (1) CA2649070C (en)
DE (2) DE102006021110B4 (en)
ES (1) ES2356095T3 (en)
RU (1) RU2438874C2 (en)
WO (1) WO2007128788A1 (en)

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CN103507277B (en) * 2013-10-23 2015-06-17 连云港中复连众复合材料集团有限公司 Improved method for layering of root of blade of wind driven generator
WO2015092364A1 (en) 2013-12-19 2015-06-25 Short Brothers Plc Fabric positioning apparatus
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DE102016002844B3 (en) * 2016-03-10 2017-08-10 Premium Aerotec Gmbh Structural component, method for producing a structural component, pressure hull for a vehicle with structural component
CN109591323B (en) * 2018-12-05 2020-10-20 中航复合材料有限责任公司 Laying device suitable for Z-shaped composite material machine body bulkhead blank
JP2022080863A (en) 2020-11-18 2022-05-30 ザ・ボーイング・カンパニー Contour enforcement for line-assembled fuselage segments
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Also Published As

Publication number Publication date
CN101426636A (en) 2009-05-06
US20100006202A1 (en) 2010-01-14
JP2009536129A (en) 2009-10-08
US8088236B2 (en) 2012-01-03
ES2356095T3 (en) 2011-04-04
EP2015922A1 (en) 2009-01-21
EP2015922B1 (en) 2010-11-24
CN101426636B (en) 2012-09-05
DE102006021110B4 (en) 2011-04-21
ATE489221T1 (en) 2010-12-15
CA2649070C (en) 2012-11-20
RU2008142970A (en) 2010-06-10
JP5027215B2 (en) 2012-09-19
WO2007128788A1 (en) 2007-11-15
DE602007010760D1 (en) 2011-01-05
DE102006021110A1 (en) 2007-11-08
BRPI0712293A2 (en) 2012-01-10
RU2438874C2 (en) 2012-01-10

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Effective date: 20180504